System and method for reconfiguring a bleed system

ABSTRACT

A system includes a bleed system configured to direct a bleed flow from a compressor section to an exhaust section of a gas turbine engine. The bleed system includes a first bleed conduit section configured to couple to the compressor section, a second bleed conduit section configured to couple to the exhaust section, and a first rotatable joint coupling together adjacent conduits of the first and second bleed conduit sections. The second bleed conduit section has components configured to rotate between a plurality of configurations relative to the first bleed conduit section and the compressor section via the first rotatable joint. The plurality of orientations corresponds to a plurality of exhaust outlet orientations of the exhaust section, and the components of the second bleed conduit section are the same in each orientation.

BACKGROUND

The subject matter disclosed herein relates to a gas turbine system and,more particularly, a bleed system for a compressor of the gas turbinesystem.

A gas turbine system includes a compressor, a combustor, and a turbine.The compressor compresses an intake air in one or more stages to producea compressed air. The combustor mixes the compressed air with fuel andcombusts the fuel with the compressed air to generate hot combustiongases. The turbine directs the hot combustion gases through one or moreturbine stages to drive rotation of a shaft, which may be coupled to thecompressor and a load. Additionally, the gas turbine system may bleed aportion of the compressed air through a conduit of a bleed system to atarget location different from the combustor. Unfortunately, the targetlocation may be different in various configurations of the gas turbinesystem, which may result in the need for different conduit designs toaccommodate each of the various configurations of the gas turbinesystem. Accordingly, a need exists for a bleed system configured to movebetween different configurations and associated target locations in thegas turbine system, thereby reducing part count inventory.

BRIEF DESCRIPTION

Certain embodiments commensurate in scope with the originally claimedsubject matter are summarized below. These embodiments are not intendedto limit the scope of the claimed subject matter, but rather theseembodiments are intended only to provide a brief summary of possibleforms of the subject matter. Indeed, the subject matter may encompass avariety of forms that may be similar to or different from theembodiments set forth below.

In certain embodiments, a system includes a bleed system configured todirect a bleed flow from a compressor section to an exhaust section of agas turbine engine. The bleed system includes a first bleed conduitsection configured to couple to the compressor section, a second bleedconduit section configured to couple to the exhaust section, and a firstrotatable joint coupling together adjacent conduits of the first andsecond bleed conduit sections. The second bleed conduit section isconfigured to rotate between a plurality of orientations relative to thefirst bleed conduit section and the compressor section via the firstrotatable joint. The plurality of orientations correspond to a pluralityof exhaust outlet orientations of the exhaust section.

In certain embodiments, a method includes coupling together, via a firstrotatable joint, adjacent conduits of first and second bleed conduitsections of a bleed system configured to direct a bleed flow from acompressor section to an exhaust section of a gas turbine engine,wherein the first bleed conduit section is configured to couple to thecompressor section, and the second bleed conduit section is configuredto couple to the exhaust section. The method further includes rotating,via the first rotatable joint, the second bleed conduit section betweena plurality of orientations relative to the first bleed conduit sectionand the compressor section, wherein the plurality of orientationscorrespond to a plurality of exhaust outlet orientations of the exhaustsection.

In certain embodiments, a system includes a compressor section of a gasturbine engine, an exhaust section of the gas turbine engine, and ableed system configured to direct a bleed flow from the compressorsection to the exhaust section. The bleed system includes a first bleedconduit section coupled to the compressor section, a second bleedconduit section coupled to the exhaust section, and a first rotatablejoint coupling together adjacent conduits of the first and second bleedconduit sections. The second bleed conduit section is configured torotate between a plurality of orientations relative to the first bleedconduit section and the compressor section via the first rotatablejoint, wherein the plurality of orientations correspond to a pluralityof exhaust outlet orientations of the exhaust section.

BRIEF DESCRIPTION OF THE DRAWINGS

These and other features, aspects, and advantages of the presentdisclosure will become better understood when the following detaileddescription is read with reference to the accompanying drawings in whichlike characters represent like parts throughout the drawings, wherein:

FIG. 1 is a schematic diagram of an embodiment of a gas turbine systemhaving a bleed system configured to reorient in a plurality of differentpositions to accommodate different configurations of an exhaust section;

FIG. 2 is a schematic side view of an embodiment of the bleed system ofFIG. 1 , illustrating a plurality of orientations of a second bleedconduit section relative to a first bleed conduit section coupled to acompressor section;

FIG. 3 is a schematic cross-sectional view of an embodiment of arotatable joint configured to enable rotation between the first andsecond bleed conduit sections of the bleed system of FIGS. 1 and 2 ;

FIG. 4 is a cross-sectional view of an embodiment of the rotatable jointof FIG. 3 , further illustrating details of an annular clamp configuredto enable loosening, tightening, rotation, and separation of adjacentconduits connected at the rotatable joint;

FIG. 5 is a schematic view of an embodiment of a valve assembly and amounting bracket configured to be disconnected and reconnected indifferent configurations via rotatable joints and removable flanges;

FIG. 6 is a partial perspective view of an embodiment of the bleedsystem coupled to the exhaust section of the gas turbine system of FIG.1 , further illustrating details of the second bleed conduit section ina first configuration relative to the first bleed conduit section; and

FIG. 7 is a partial perspective view of an embodiment of the bleedsystem of FIG. 6 , further illustrating a reorientation of the secondbleed conduit section relative to the first bleed conduit section toaccommodate a different configuration of the exhaust section.

DETAILED DESCRIPTION

One or more specific embodiments of the present disclosure will bedescribed below. In an effort to provide a concise description of theseembodiments, all features of an actual implementation may not bedescribed in the specification. It should be appreciated that in thedevelopment of any such actual implementation, as in any engineering ordesign project, numerous implementation-specific decisions must be madeto achieve the developers' specific goals, such as compliance withsystem-related and business-related constraints, which may vary from oneimplementation to another. Moreover, it should be appreciated that sucha development effort might be complex and time consuming, but wouldnevertheless be a routine undertaking of design, fabrication, andmanufacture for those of ordinary skill having the benefit of thisdisclosure.

When introducing elements of various embodiments of the presentdisclosure, the articles “a,” “an,” “the,” and “said” are intended tomean that there are one or more of the elements. The terms “comprising,”“including,” and “having” are intended to be inclusive and mean thatthere may be additional elements other than the listed elements.

A variety of systems, such as compressors, pumps, turbines, and variousturbomachines may use a bleed system to bleed a fluid from one locationto another. The bleed system may receive a bleed flow from a highpressure region and direct the bleed flow to a low pressure region. Asdiscussed in detail below, the present bleed system includes a singleset of components, which are configured to move between a plurality ofdifferent configurations, such as different exhaust outlet orientations(e.g., left hand exhaust outlet, right hand exhaust outlet, and topexhaust outlet) of an exhaust section. In other words, rather than usinga different bleed system for each exhaust outlet orientation, thedisclosed embodiments use the same bleed system (e.g., a single assemblyof components) in multiple configurations of the same components,thereby providing a universal bleed system that can accommodate 2, 3, 4,5, or more different configurations of the exhaust section.

Specifically, the present bleed system includes one or more rotationaljoints, which enable conduit sections to rotate about an axis. The bleedsystem also includes one or more mounting flanges, which can bereconfigured in different mounting configurations. A first bleed conduitsection of the bleed system may remain in a fixed position relative to acompressor section of the gas turbine system, whereas a second bleedconduit section (or multiple bleed conduit sections) may be moved (e.g.,rotated) and/or reconfigured to change a target location for deliveringa bleed flow. The bleed system also includes a plurality of flexibleand/or movable structures (e.g., gimbals, spring hangers, hinges,flexible conduits, and/or rotatable joints) configured to enable freedomof movement to accommodate thermal expansion and contraction and toprovide flexibility when reconfiguring the bleed system between aplurality of configurations (e.g., different exhaust outletorientations). Details of the bleed system are discussed in furtherdetail below with reference to FIGS. 1-7 .

FIG. 1 is a block diagram of an embodiment of a gas turbine system 10having a gas turbine engine 12 to which a bleed system 14 is coupled. Inthe illustrated embodiment, the bleed system 14 extends between a highpressure region 16 and a low pressure region 18 of the gas turbinesystem 10. The bleed system 14 is configured to route a bleed flowbetween the high pressure region 16 and the low pressure region 18 in avariety of configurations of the gas turbine engine 12. In particular,the bleed system 14 is configured to move (e.g., rotate) between aplurality of orientations (e.g., angular orientations) about a centralaxis 20 of the gas turbine system 10, thereby enabling the same bleedsystem 14 to be used with various configurations of the gas turbinesystem 10, such as different configurations of an exhaust section 22(e.g., different exhaust outlet orientations, such as exhaust outlets 82directed crosswise to the central axis 20). Without the disclosedembodiments of the bleed system 14, a different bleed system may benecessary for each different configuration of the exhaust section 22,which would result in substantially greater manufacturing costs. Thedisclosed embodiments reduce the number of different bleed systems byincorporating a multi-configuration (e.g., multi-orientation) featureinto the design of the bleed system 14.

The gas turbine engine 12 includes an air intake section 24, acompressor section 26, a combustion section 28, a turbine section 30,the exhaust section 22, and a load 32, such as an electrical generator.The gas turbine engine 12 also may include one or more controllers 34having one or more processors 36, memory 38, and instructions 40 storedon the memory 38 and executable by processors 36 to perform variouscontrol functions of the gas turbine system 10 and the bleed system 14.For example, the controller 34 may be configured to control one or morevalves of the bleed system 14 to control a bleed flow between the highand low pressure regions 16 and 18. The air intake section 24 mayinclude one or more air filters, fluid injection systems (e.g., heatedfluids and/or cooled fluids), anti-icing systems, silencer baffles, orany combination thereof. The air intake section 24 routes an air flow 42into one or more compressor stages 44 of a compressor section 26.

The compressor section 26 includes a compressor casing 46, one or morevanes 48 extending inwardly from the compressor casing 46 in each of thecompressor stages 44, one or more blades 50 extending outwardly from ashaft 52 in each of the compressor stages 44, and connections 54 withthe bleed system 14. The shaft 52 is configured to rotate a plurality ofcircumferentially spaced blades 50 in each of the compressor stages 44,while a plurality of circumferentially spaced vanes 48 remain stationaryin each of the compressor stages 44. The connections 54 may includefluid conduit connections with the bleed system 14, such as connections54 at one or more of the compressor stages 44. The connections 54 may bedisposed on opposite sides (e.g., diametrically opposite sides) of thecompressor casing 46, or in any suitable location on the compressorcasing 46. The compressor section 26 outputs a compressed air flow 56into one or more combustors 58 of the combustion section 28.

Each combustor 58 includes one or more fuel nozzles 60, which areconfigured to route the compressed air 56 and fuel 62 from a fuel supplysystem 64 into a combustion chamber 66 of the combustor 58. The fuel 62and the compressed air 56 mix and combust within the combustion chamber66, thereby producing hot combustion gases 68 that are routed into theturbine section 30. In certain embodiments, the combustion section 28has a single annular combustor 58 disposed circumferentially about acentral axis of the gas turbine system 10. However, in some embodiments,the combustion section 28 includes a plurality of combustors 58 (e.g.,combustor cans) spaced circumferentially about the central axis of thegas turbine system 10. The fuel nozzles 60 may include 1, 2, 3, 4, 5, 6,or more fuel nozzles, which may be configured to operate on one or morefuel circuits. The fuel circuits may be designed to deliver the samefuel or different fuels, such as liquid and gas fuels. Regardless, oncethe fuel combusts, the hot combustion gases 68 are used to drive theturbine section 30.

The turbine section 30 includes a plurality of turbine stages 70configured to gradually expand the hot combustion gases 68 and drivecomponents of the gas turbine system 10. The turbine section 30 includesa turbine casing 72, one or more turbine vanes 74 extending inwardlyfrom the turbine casing 72 in each of the turbine stages 70, and one ormore turbine blades 76 extending outwardly from a turbine shaft 78 ineach of the one or more turbine stages 70. The turbine shaft 78 isdriven to rotate by the hot combustion gases 68 flowing against aplurality of circumferentially spaced turbine blades 76 in each of theturbine stages 70, while a plurality of circumferentially spaced turbinevanes 74 remain stationary in each of the turbine stages 70. The hotcombustion gases 68 expand through the turbine section 30 while drivingrotation of the turbine blades 76 and turbine shaft 78 and thendischarge through the exhaust section 22.

The exhaust section 22 includes an exhaust plenum 80 disposed downstreamfrom the turbine section 30, and the exhaust plenum 80 includes anexhaust outlet 82. The exhaust outlet 82 may be positioned in a varietyof exhaust outlet orientations depending on the particular configurationof the gas turbine system 10. In the illustrated embodiment, the exhaustoutlet 82 is arranged in a right-hand orientation or configuration 84 ona right-hand side of the exhaust plenum 80 (when viewed from an aft endof the gas turbine system 10), thereby directing an exhaust flow in aright hand direction as indicated by arrows 86. However, the exhaustoutlet 82 may be arranged in other configurations (shown in phantomlines in FIG. 1 ), such as a top orientation or configuration 88 todirect a vertical flow of the exhaust gas, or a left-hand orientation orconfiguration 90 configured to direct the exhaust flow in a left-handdirection as indicated by arrows 92. As discussed in further detailbelow, the bleed system 14 may be rotated or moved between theright-hand configuration 84, the top configuration 88, and/or theleft-hand configuration 90 to accommodate different exhaust outletorientations of the exhaust outlet 82 while using the same components ofthe bleed system 14.

In operation, the gas turbine engine 12 receives air through the airintake section 24, compresses the air in one or more compressor stages44 via rotation of a plurality of compressor blades 50 in each of thecompressor stages 44, and then routes the compressed air 56 into one ormore combustors 58 of the combustion section 28. The combustors 58combust the fuel 62 with the compressed air 56 via injection through thefuel nozzles 60 and combustion within the combustion chamber 66, andthen route the hot combustion gases 68 into one or more turbine stages70. The turbine stages 70 use the energy of the hot combustion gases 68to drive a plurality of turbine blades 76 in each of the turbine stages70, thereby driving rotation of the turbine shaft 78. In turn, theturbine shaft 78 drives rotation of a common shaft 94 between theturbine section 30 and the compression section 26, thereby driving theshaft 52 of the compressor section 26. The rotation of the turbine shaft78 also drives rotation of a shaft 96 coupled to the load 32, which maybe an electrical generator to generate electricity for a local facilityor the power grid. In operation, the controller 34 is configured tocontrol a fuel flow from the fuel supply system 64, a bleed flow throughthe bleed system 14, and other aspects of the gas turbine system 10.

The bleed system 14 is configured to route a compressed air stream fromthe high pressure region 16, which may include the compressor section26, to the low pressure region 18, which may include the exhaust plenum80 of the exhaust section 22. However, the bleed system 14 may be usedbetween other high and low pressure regions of the gas turbine system10. In the illustrated embodiment, the bleed system 14 includes a firstbleed conduit section 100 fluidly coupled to the compressor section 26via the connections 54, and a second bleed conduit section 102 movably(e.g., rotatably) coupled to the first bleed conduit section 100 andmovably coupled to the exhaust section 22. The first and second bleedconduit sections 100 and 102 may include a plurality of flexible and/ormovable structures, which are configured to provide freedom of movementin one or more directions (e.g., rotational direction, horizontaldirection, and/or vertical direction). The flexible and/or movablestructures may include, for example, one or more gimbals 104, one ormore spring hangers 106, one or more flexible conduits or hoses, and oneor more rotatable joints 108. The flexible and/or movable structures(e.g., 104, 106, and 108) may be configured to enable freedom ofmovement to accommodate thermal expansion and contraction in the bleedsystem 14 and between components of the gas turbine system 10, and toprovide flexibility when reconfiguring the bleed system 14 between aplurality of configurations (e.g., different orientations of the secondbleed conduit section 102 according to the exhaust section 26configuration, such as configurations 84, 88, and 90 of the exhaustoutlet 82). Additionally, the first and second bleed conduit sections100 and 102 may include one or more mounting brackets 110, a stagedexpansion conduit 112, an outlet section 114, one or more straightconduits 116 between the various components, and one or more bendingconduits or elbows 118 between the various components.

As discussed in further detail below, the first bleed conduit section100 may have a U-shaped conduit configuration 120 configured topartially extend around opposite sides of the compressor section 26before fluidly connecting with the internal fluid flow through thecompressor section 26 via the connections 54. The U-shaped conduitconfiguration 120 of the first bleed conduit section 100 includes acentral straight section or straight conduit 124 generally centered andoriented crosswise relative to the central axis 20, gimbals 126 and 128coupled to opposite ends of the straight conduit 124, bending conduitsor elbows 130 and 132 coupled to the respective gimbals 126 and 128,gimbals 134 and 136 coupled to the respective bending conduits or elbows130 and 132, and the connections 54 between the gimbals 134 and 136 andthe compressor casing 46 of the compressor section 26. In theillustrated embodiment, the U-shaped conduit configuration 120 mayremain in a fixed orientation once mounted to the compressor casing 46,while the J-shaped conduit configuration 122 of the second bleed conduitsection 102 may be reoriented or rotated about the central axis 20 toaccommodate the different configurations 84, 88, and 90 of the exhaustoutlet 82.

Additionally, the second bleed conduit section 102 may include aJ-shaped conduit configuration 122, which extends from the first bleedconduit section 100 and turns toward and connects with the exhaustplenum 80 of the exhaust section 22 at the staged expansion conduit 112and the outlet section 114. The J-shaped conduit configuration 122 ofthe second bleed conduit section 102 includes a straight conduit 138coupled to the central straight conduit 124 in a generally crosswiseorientation along the central axis 20 and a rotational joint 140 coupledto the straight conduit 138. The J-shaped conduit configuration 122 alsoincludes a bending conduit or elbow 142 coupled to the rotational joint140, a gimbal 144 coupled to the bending conduit or elbow 142 via anintermediate straight conduit 146, and a straight conduit 148 coupled tothe gimbal 144 opposite the intermediate straight conduit 146. TheJ-shaped conduit configuration 122 also includes a bending conduit orelbow 150 coupled to the straight conduit 148, one or more springhangers 152 coupled to one or both of the conduits 148 and 150, and agimbal 154 coupled to the bending conduit or elbow 150. The J-shapedconduit configuration 122 also includes a straight conduit 156 coupledto (and extending between) the gimbal 154 and a gimbal 158 and aplurality of spring hangers 160 coupled to the straight conduit 156 viaan intermediate bracket 162. The J-shaped conduit configuration 122 alsoincludes a rotatable joint 164 removably coupled between a straightconduit 166 coupled to the gimbal 158 and a straight conduit 168 coupledto a valve assembly 170. The J-shaped conduit configuration 122 alsoincludes a rotatable joint 172 removably coupled between a straightconduit 174 coupled to the valve assembly 170 and a straight conduit 176coupled to a gimbal 178. The J-shaped conduit configuration 122 alsoincludes a straight conduit 180 coupled to the gimbal 178 opposite thestraight conduit 176, and the staged expansion conduit 112 is coupled tothe straight conduit 180 and extends to the outlet section 114 in theexhaust section 22.

The valve assembly 170 may include one or more valves 182 driven by anactuator 184, which is communicatively coupled to and controlled by thecontroller 34. For example, the valve 182 may include a gate valve, aball valve, a flapper valve, or any combination thereof. The actuator184 may include an electric drive or motor, a solenoid, a pneumaticdrive, a hydraulic drive, or any combination thereof. Accordingly, thecontroller 34 may control the actuator 184 to open and close the valve182, thereby controlling a bleed flow through the bleed system 14,including the bleed flow through both the first and second conduitsections 100 and 102 between the high pressure region 16 in thecompressor section 26 and the low pressure region 18 in the exhaustsection 22. The valve assembly 170 also may include a protective shield,a tray to collect fluid spills or leaks, and/or a wall structure 186 atleast partially or entirely extending around the valve 182 and/or theactuator 184.

The shield 186 of the valve assembly 170 also may be coupled to anenclosure 188 of the gas turbine engine 12 via a mounting bracket 190.In certain embodiments, the mounting bracket 190 may extend between andcouple with the enclosure 188 and the valve assembly 170, the straightconduit 168, the straight conduit 174, and/or some other portion of thesecond bleed conduit section 102. The enclosure 188 may substantially orcompletely surround the compressor section 26, the combustion section28, and the turbine section 30 of the gas turbine engine 12, and themounting bracket 190 may rigidly support the valve assembly 170 and thesecond bleed conduit section 102 relative to a sidewall 192 of theenclosure 188. The mounting bracket 190 may include a plurality ofbracket sections 194 coupled together with intermediate flanges 196. Forexample, the flanges 196 may be bolted together with a plurality ofthreaded fasteners, such as threaded bolts and nuts.

As discussed in detail below, the mounting bracket 190 may be removed,reoriented, and reinstalled when moving the J-shaped conduitconfiguration 122 of the second bleed conduit section 102 betweendifferent configurations for the different configurations 84, 88, and 90of the exhaust outlet 82. In FIG. 1 , the bleed system 14 is illustratedin an alternative configuration 198 as indicated by dashed lines. Thealternative configuration 198 corresponds to the left-hand configuration90 of the exhaust outlet 82 of the exhaust section 22. In particular, asdiscussed in detail below, the J-shaped conduit configuration 122 of thesecond bleed conduit section 102 is configured to rotate from theillustrated bleed conduit orientation or configuration 200 shown insolid lines to the alternative bleed conduit orientation orconfiguration 198 shown in dashed lines via rotation about the rotatablejoint 140 disposed along the central axis 20, thereby enabling theJ-shaped conduit configuration 122 to provide a similar or substantiallyidentical configuration for either the right-hand configuration 84 ofthe exhaust outlet 82 and the left-hand configuration 90 of the exhaustoutlet 82. In certain embodiments, one of the illustrated configurations198 and 200 may be used for multiple configurations of the exhaustoutlet 82, such as both the right-hand configuration 84 and the topconfiguration 88. The different configurations of the J-shaped conduitconfiguration 122 are discussed in greater detail below with referenceto FIG. 2 .

As further illustrated in FIG. 1 , the staged expansion conduit 112includes a plurality of alternating constant-diameter conduits 202 andexpanding-diameter conduits 204, thereby defining a plurality of stagesof expansion and depressurization. In particular, the illustrated stagedexpansion conduit 112 includes, in series, an expanding conduit 206, aconstant conduit 208, an expanding conduit 210, a constant conduit 212,and an expanding conduit 214. The conduits 206, 208, 210, 212, and 214progressively increase in diameter and cross-sectional area, whereineach constant conduit 208 and 212 has a constant diameter andcross-sectional area, and each expanding conduit 206, 210, and 214 has agradually increasing diameter and cross-sectional area in a direction ofbleed flow. The expanding conduit 214 is coupled to an end wall 216 ofthe exhaust section 122 between the enclosure 188 and the exhaust plenum80. The expanding conduit 214 also leads into the outlet section 114,which is disposed inside of the exhaust plenum 80. At a connectionbetween the staged expansion conduit 112 and the end wall 216, the bleedsystem 14 may enable freedom of movement in one or more directions, suchaxial, radial, and/or rotational directions of movement relative to theend wall 216. The outlet section 114 includes a plurality of outlets 218disposed in an annular housing 220, wherein the outlets 218 areconfigured to distribute or diffuse the bleed flow from the bleed system14 into the exhaust plenum 80. For example, the outlets 218 may bedisposed along a sidewall 222 (e.g., annular sidewall) and an end wall224 (e.g., axially facing end wall) of the annular housing 220. Incertain embodiments, the connection between the end wall 216 and thestaged expansion conduit 112 and/or the outlet section 114 may include amoveable joint configured to enable axial movement and/or rotationtherebetween.

The staged expansion conduit 112 is configured to gradually depressurizethe bleed flow to reduce the vibration and/or noise of the bleed system14, such as vibration of a bleed valve. The staged expansion conduit 112may have at least two stages configured to gradually (e.g.,incrementally) depressurize the bleed flow. Each stage of the stagedexpansion conduit 112 may have an expansion section and/or a diffuserplate. The number of stages may be determined at least in part on thedifference in pressure between the high pressure region 16 and the lowpressure region 18. More stages may be used for large pressuredifferences than for small pressure differences. The expansion sectionsincrease the dimension of the staged expansion conduit 112 to at leastreduce the static pressure of the bleed flow. The diffuser platespartially obstruct the bleed flow and permit passage of the bleed flowthrough orifices. The diffuser plates are configured to at least reducethe kinetic energy or dynamic pressure of the bleed flow. Thecharacteristics of the expansion sections (e.g., expansion percentage,size, cross-sectional shape, length) and diffuser plates (e.g., orificesize, orifice quantity, orifice shape, orifice configuration, diffuserplate size) affect the vibration of the bleed system 14.

Vibration and thermal expansion/contraction of the bleed system 14 maycause the bleed system 14 to move. Certain mounting and couplingfeatures may be utilized to accommodate the movements of the bleedsystem 14. For example, the various components of the bleed system 14may be configured to allow for movement in one or more directions, suchas an axial direction along an axis of the conduit, rotationally aboutthe axis of the conduit, in a horizontal direction, a verticaldirection, or any combination thereof. Each gimbal 104 may be configuredto allow for axial movement, rotational movement, or any combinationthereof, relative to an axis of the adjacent conduits. The rotatablejoints 108 are configured to enable rotation about an axis of theadjacent conduits. The rotatable joints 108 also may be configured toenable separation and reattachment of the adjacent conduits. The springhangers 106 are configured to enable movement along an axis of thespring portion of the spring hangers, which may be oriented in avertical direction, a horizontal direction, or any other suitableangular direction between horizontal and vertical within the enclosure188 of the gas turbine engine 12. For example, each of the springhangers 106 may be hung from a top wall or ceiling of the enclosure 188,thereby allowing some vertical movement of the various conduits andsections of the bleed system 14. Additionally, as discussed above, thegimbals 104, the rotatable joints 108, and the spring hangers 106 (e.g.,flexible and/or movable structures) are configured to help enablereconfiguration of the bleed system 14 between different configurations,such as different orientations of the second bleed conduit section 102to accommodate the different exhaust outlet orientations (e.g., 86, 88,and 90).

In the illustrated embodiment, when reconfiguring the bleed system 14between the configurations 198 and 200 of the J-shaped conduitconfiguration 122 of the second bleed conduit section 102, the rotatablejoint 140 may be loosened to enable rotation of the second bleed conduitsection 102 about the central axis 20, such that the second bleedconduit section 102 moves from the configuration 200 to theconfiguration 198 (or vice versa). Additionally, the rotatable joints164 and 172 may be loosened and disconnected to allow reorientation ofthe valve assembly 170 and the mounting bracket 190, thereby enablingthe valve assembly 170 and the mounting bracket 190 to be oriented in aproper configuration to mount against the sidewall 192 of the enclosure188 on the opposite side of the enclosure 188, as illustrated by thealternative configuration 198. In the illustrated embodiment, therotatable joint 140 is aligned with the central axis 20 (e.g., in acommon vertical plane with the central axis 20), thereby enabling theJ-shaped conduit configuration 122 of the second bleed conduit section102 to rotate between a plurality of symmetrical configurations, such asthe configurations 198 and 200.

FIG. 2 is a schematic view of an embodiment of the gas turbine engine 12and the bleed system 14 taken in a plane perpendicular to the centralaxis 20 of FIG. 1 , further illustrating details of the differentconfigurations of the bleed system 14. In the illustrated embodiment,the first bleed conduit section 100 has the gimbals 126, 128, 134, and136, and the conduits 124, 130, 132 arranged in the U-shaped conduitconfiguration 120, which partially wraps around opposite sides of thecompressor casing 46 of the compressor 26. The U-shaped conduitconfiguration 120 may be symmetric relative to the rotatable joint 140and/or the plane perpendicular to the central axis 20 (e.g., the planethrough the central axis 20 and the rotatable joint 140). Theconnections 54 include conduits 230 fluidly and mechanically coupled tothe compressor casing 46 via mounting flanges 232. The mounting flanges232 may be coupled to the compressor casing 46 via one or morefasteners, such as threaded fasteners (e.g., bolts), welded joints,brazed joints, clamps, dovetail joints, or other removable or fixedjoints.

The first bleed conduit section 100 is configured to receive a bleedflow 234 (e.g., a compressed air flow) from the high pressure region 16inside the compressor section 26 and to route the bleed flow through thevarious conduits 230, 130, 132, and 124 into the second bleed conduitsection 102, which connects with the first bleed conduit section 100 viathe rotatable joint 140. Again, each of the gimbals 104, includinggimbals 126, 128, 134, and 136, is configured to enable movement (e.g.,expansion and contraction) in an axial direction relative to theadjacent conduits, rotation about the axis of the adjacent conduits, orany combination thereof.

When reconfiguring the bleed system 14 between different configurations,the second bleed conduit section 102 is configured to rotate about therotatable joint 140 as indicated by the bleed conduit orientations orconfigurations 198, 200, 236, 238, and 240. The configurations 198 and200 correspond to the configurations shown and described above withreference to FIG. 1 . The configuration 236 is oriented midway betweenthe configurations 198 and 200, such that the second bleed conduitsection 102 is substantially perpendicular relative to the second bleedconduit sections 102 in the configurations 198 and 200. Theconfigurations 238 and 240 are approximately midway between theconfigurations 200 and 236 and the configurations 198 and 236,respectively. However, the second bleed conduit section 102 may berotated about the rotational joint 140 to any angular orientation asindicated by arrows 242. In FIG. 2 , the various components of thesecond bleed conduit section 102 are removed for simplicity; however,the second bleed conduit section 102 may include each of the componentsdiscussed above with reference to FIG. 1 . For example, the flexibleand/or movable structures (e.g., gimbals 104, spring hangers 106, androtatable joints 108) are configured to provide flexibility in the firstand second bleed conduit sections 100 and 102 when reconfiguring (e.g.,rotating) the second bleed conduit section 102 as illustrated in FIG. 2.

FIG. 3 is a schematic cross-sectional side view of one of the rotatablejoints 108, such as the rotatable joints 140, 164, and 172, of thesecond bleed conduit section 102 of FIG. 1 . The rotatable joint 108 mayinclude an annular clamp 250 disposed about a male joint portion 252inserted within a female joint portion 254. The male joint portion 252is disposed at an end portion 256 of a conduit 258, while the femalejoint portion 254 is disposed on an end portion 260 of a conduit 262.The male joint portion 252 may include an annular outer lip 264protruding radially outwardly from the conduit 258, and an axiallyextending annular portion 266 projecting at the end portion 256. Thefemale joint portion 254 may include an annular outer lip 268 protrudingradially outwardly from the conduit 262 and an axially recessed annularportion or cavity 270 disposed inwardly into the end portion 260. Themale joint portion 252 has the axially extending annular portion 266inserted into the axially recessed annular portion 270, while theannular clamp 250 extends circumferentially around both of the annularouter lips 264 and 268.

The annular clamp 250 is configured to compressively secure the annularouter lips 264 and 268 and to hold together the connection between theaxially extending annular portion 266 and the axially recessed annularportion 270. When the annular clamp 250 is tightened about the annularouter lips 264 and 268, the rotatable joint 108 may be held in a fixedrotational position between the conduits 258 and 262, such that theconduits 258 and 262 cannot rotate relative to one another. However, theannular clamp 250 may be loosened and/or removed to enable movement(e.g., rotation) between and/or separation of the conduits 258 and 262.For example, by loosening the annular clamp 258, the conduits 258 and262 may be rotated relative to one another as indicated by arrows 272about a central axis 274 of the rotatable joint 108. As discussed aboveand in further detail below, the rotatable joint 108 is configured toenable rotation between the different configurations 198, 200, 236, 238,and 240 of the second bleed conduit section 102 relative to the firstbleed conduit section 100, and also to enable reconfiguration of thevalve assembly 170 and the mounting bracket 190.

FIG. 4 is a cross-sectional side view of the rotatable joint 108 asillustrated in FIG. 3 , further illustrating details of the annularclamp 250 disposed about the male joint portion 252 and the female jointportion 254 of the conduits 258 and 262. As illustrated, the annularclamp 250 includes a plurality of clamp sections, such as semi-annularclamp sections 280 and 282 (e.g., C-shaped clamp sections). Thesemi-annular clamp sections 280 and 282 are disposed about the male andfemale joint portions 252 and 254, and the semi-annular clamp sections280 and 282 are coupled together via fasteners 284 disposed in adjacentflanges 286 and 288 of the respective semi-annular clamp sections 280and 282. The fasteners 284 may include threaded bolts 290 extendingthrough bolt holes 292 and 294 in the respective flanges 286 and 288,through which the threaded bolts 290 connect with threaded nuts 296 tocompressively secure the flanges 286 and 288 together. In theillustrated embodiment, the annular clamp 250 includes the twosemi-annular clamp sections 280, and two sets of mating flanges 286 and288. In some embodiments, the annular clamp 250 may include a split-ringclamp having a single set of flanges 286 and 288 at a single break inthe annular clamp 250, or the annular clamp 250 may include a greaternumber (e.g., 3, 4, 5, or more) of clamp sections and associated flanges286 and 288.

The fasteners 284 are configured to compressively couple together thesemi-annular clamp sections 280 and 282 about the male and female jointportions 252 and 254, thereby limiting rotational movement between theconduits 258 and 262. However, the fasteners 284 may be loosened toenable movement (e.g., rotation movement) between the male and femalejoint portions 252 and 254 and thus rotational movement between theconduits 258 and 262. When reconfiguring the second bleed conduitsection 102 between the different configurations 198, 200, 236, 238, and240, the fasteners 284 may be loosened sufficiently to enable easierrotation of the second bleed conduit section 102 about the rotationaljoint 140. Likewise, the rotational joints 164 and 172 may be loosenedvia loosening of the fasteners 284, thereby enabling reorientation ofthe valve assembly 170 and the mounting bracket 190 between thedifferent configurations of the second bleed conduit section 102.

FIG. 5 is a schematic view of an embodiment of the valve assembly 170,the mounting bracket 190, and the rotational joints 164 and 172 disposedbetween the straight conduits 166 and 168 and the straight conduits 174and 176. The valve assembly 170 may be moved between a plurality oforientations via disconnection and/or rotational movement at therotatable joints 164 and 172 when reconfiguring the second bleed conduitsection 102 relative to the first bleed conduit section 100. In theillustrated embodiment, the reorientation of the valve assembly 170 isperformed by loosening and/or disconnecting each of the rotatable joints164 and 172, which may have the features of the rotatable joint 108 asdiscussed above with reference to FIGS. 3 and 4 . For example, the valveassembly 170 may be rotated about an axis of the straight conduits 166,168, 174, and 176, such as rotation between 0 and 360 degrees about theaxis.

The valve assembly 170 also may be reoriented along with the mountingbracket 190. The mounting bracket 190 includes a mounting bracket or arm300 coupled to the shield 186 of the valve assembly 170, wherein themounted bracket or arm 300 includes a flange 302 having fastenerreceptacles 304. The mounting bracket 190 also includes a mountingbracket or arm 306 having flanges 308 and 310 on opposite ends of thearm 306. The flange 308 includes fastener receptacles 312, while theflange 310 includes fastener receptacles 314. The flanges 302 and 308 ofthe arms 300 and 306 are configured to removably couple together viathreaded fasteners 316 (e.g., threaded bolts) extending through thefastener receptacles 304 and 312 and connecting with mating threadedfasteners 318 (e.g., threaded nuts). Similarly, the flange 310 isconfigured to mount to the side wall 192 of the enclosure 188 of the gasturbine engine 12 as illustrated in FIG. 1 by extending threadedfasteners 320 (e.g., threaded bolts) through the fastener receptacles314 into the sidewall 192.

The illustrated fasteners 316, 318, and 320 are removable threadedfasteners, which may include any number of threaded bolts and nuts. Incertain embodiments, the fasteners 316, 318, and 320 may include othertypes of threaded fasteners and/or removable fasteners, such asfastening clamps, spring-loaded fasteners, dovetail joints, hingedjoints, or any combination thereof. Accordingly, the removability of thefasteners 316, 318, and 320 is configured to enable reconfiguration ofthe mounting bracket 190 when changing the valve assembly 170 and theentire second bleed conduit section 102 between the differentconfigurations, such as configurations 198, 200, 236, 238, and 240. Asfurther illustrated in FIG. 5 , the controller 34 is configured tooperate the actuator 184 to open and close the valve 182 in the valveassembly 170. The valve 182 may include a valve element 320 (e.g., ball,gate, flapper, etc.) coupled to the actuator 184 via a valve stem 322.For example, the actuator 184 may rotate and/or axially move the valvestem 322 to move the valve element 320 between open and closed positionsbetween the straight conduits 168 and 174.

FIG. 6 is a partial perspective view of the gas turbine system 10 andthe bleed system 14 of FIGS. 1-5 , further illustrating details of thebleed system 14 coupled to the exhaust section 22 in the configuration200 of the second bleed conduit section 102 and the right-handconfiguration 84 of the exhaust outlet 82. In certain embodiments, theconfiguration 200 of the second bleed conduit section 102 as illustratedin FIG. 6 also may be used for the top configuration 88 of the exhaustoutlet 82 as illustrated in FIG. 1 . However, any number of alternativeconfigurations of the bleed system 14 may be achieved to accommodatedifferent orientations of the exhaust outlet 82.

As illustrated in FIG. 6 , the first bleed conduit section 100 has theU-shaped conduit configuration 120 disposed in a fixed configurationrelative to the central axis 20, while the J-shaped conduitconfiguration 122 of the second bleed conduit section 102 is disposed inthe configuration 200 via rotation relative to the rotatable joint 140.The gimbals 104, the spring hangers 106, the rotatable joints 108, thestaged expansion conduit 112, the straight conduits 116, and the bendingconduits or elbows 118 of the second bleed conduit section 102 and thefirst bleed conduit section 100 are substantially the same as describedin detail above. However, in the illustrated configuration, therotatable joint 172 is disposed between the gimbal 178 and the stagedexpansion conduit 112 rearward of the gimbal 178, and the rotatablejoint 164 is disposed partially within the shield 186 of the valveassembly 170. Furthermore, the illustrated mounting bracket 190 has themounting bracket or arm 300 coupled to the straight conduit 174 ratherthan the shield 186.

When changing the configuration of the bleed system 14 and the exhaustoutlet 82, the second bleed conduit section 102 is rotated about therotatable joint 140, which is disposed along the central axis 20. One orboth of the rotatable joints 164 and 172 may be loosened and/ordisconnected to allow reorientation of the valve assembly 170 and themounting bracket 190. Additionally, the mounting brackets or arms 300and 306 may be disconnected at the flanges 302, 308, and 310, and thenreconfigured for the alternative configuration 198 as illustrated inFIG. 1 and further illustrated in FIG. 7 .

FIG. 7 is a partial perspective view of the gas turbine system 10 andthe bleed system 14 of FIGS. 1-6 , further illustrating details of thebleed system 14 coupled to the exhaust section 22 in the configuration198 of the second bleed conduit section 102 and the left-handconfiguration 90 of the exhaust outlet 82. Again, the bleed system 14has substantially the same components as FIGS. 1-6 , including thegimbals 104, the spring hangers 106, the rotatable joints 108, themounting bracket 190, the staged expansion conduit 112, the straightconduits 116, and the bending conduits or elbows 118. However, in theillustrated embodiment of FIG. 7 , the bleed system 14 has the samemodifications as discussed above with reference to FIG. 6 .

As illustrated in FIG. 7 , the second bleed conduit section 102 has beenrotated approximately 180 degrees about the central axis 20 via therotatable joint 140 as compared with the configuration 200 of FIG. 6 .In the illustrated configuration 198, the second bleed conduit section102 extends toward the exhaust section 22 with the exhaust outlet 82 inthe left-hand configuration 90. Again, the rotatable joints 164 and/or172 may be loosened or disconnected to facilitate the reorientation ofthe valve assembly 170 and the mounting bracket 190. Additionally, themounting bracket 190 may be reconfigured by disconnecting the mountingbrackets or arms 300 and 306 at the flanges 302, 308, and 310. Asillustrated in FIG. 7 , the mounting bracket 190 is directly coupled tothe straight conduit 168 rather than the shield 186 of the valveassembly 170. In particular, the mounting bracket or arm 300 is directlycoupled to the straight conduit 168. After the second bleed conduitsection 102 has been rotated from the configuration 200 of FIG. 6 to theconfiguration 198 of FIG. 7 , the rotatable joint 140 may be retightenedand secured in its rotational position, and the rotational rotatablejoints 164 and 172 may be reconnected and retightened to secure therotational position between the straight conduits 166, 168, 174 and 176.Although FIGS. 6 and 7 illustrate only the configurations 198 and 200 ofthe second bleed conduit section 102 relative to the first bleed conduitsection 100, the bleed system 14 may be reconfigured into a plurality ofpositions as discussed above with reference to FIG. 2 .

Technical effects of the disclosed embodiments include a reconfigurablebleed system, which can be used with a plurality of differentorientations of an exhaust section (e.g., left, right, and top exhaustoutlet orientations). In particular, the bleed system is reconfigurablevia a rotatable joint along a central axis, such that the bleed systemcan rotate between a plurality of different orientations takingadvantage of the symmetry about the rotatable joint. The bleed systemalso includes various flexible and/or movable structures, such asgimbals, spring hangers, and rotatable joints, configured to providefreedom of movement of the bleed system.

The subject matter described in detail above may be defined by one ormore clauses, as set forth below.

A system includes a bleed system configured to direct a bleed flow froma compressor section to an exhaust section of a gas turbine engine. Thebleed system includes a first bleed conduit section configured to coupleto the compressor section, a second bleed conduit section configured tocouple to the exhaust section, and a first rotatable joint couplingtogether adjacent conduits of the first and second bleed conduitsections. The second bleed conduit section comprises a set of componentsconfigured to rotate between a plurality of orientations relative to thefirst bleed conduit section and the compressor section via the firstrotatable joint. The plurality of orientations correspond to a pluralityof exhaust outlet orientations of the exhaust section.

The system of the preceding clause, wherein the first rotatable jointextends along a central axis of the gas turbine engine, and theplurality of orientations includes different angular orientations aboutthe central axis.

The system of any preceding clause, including the gas turbine enginehaving the compressor section, the exhaust section, a turbine section,and a combustor section.

The system of any preceding clause, wherein each of the plurality ofexhaust outlet orientations is oriented crosswise to a central axis ofthe gas turbine engine.

The system of any preceding clause, wherein the plurality of exhaustoutlet orientations includes at least one of a left-hand exhaustorientation, a right-hand exhaust orientation, or a top exhaustorientation.

The system of any preceding clause, wherein the set of components in thesecond bleed conduit section is common for each orientation of theplurality of orientations.

The system of any preceding clause, wherein the first bleed conduitsection includes a U-shaped conduit configuration.

The system of any preceding clause, wherein the U-shaped conduitconfiguration includes a central straight conduit extending betweenfirst and second bending conduits, and the central straight conduit iscoupled to the first rotatable joint.

The system of any preceding clause, wherein the first bleed conduitsection includes a plurality of gimbals disposed along one or more ofthe central straight conduit, the first bending conduit, or the secondbending conduit.

The system of any preceding clause, wherein the second bleed conduitsection includes a J-shaped conduit configuration.

The system of any preceding clause, wherein the second bleed conduitsection includes one or more gimbals and one or more spring hangers.

The system of any preceding clause, wherein the second bleed conduitsection includes a staged expansion conduit having a plurality ofexpanding conduits arranged in stages along a direction of a bleed flowthrough the bleed system.

The system of any preceding clause, wherein the second bleed conduitsection includes a mounting bracket configured to mount the second bleedconduit section to a wall of an enclosure of the gas turbine engine.

The system of any preceding clause, wherein the second bleed conduitsection includes a second rotatable joint and a third rotatable jointdisposed along a conduit of the second bleed conduit section upstreamand downstream of the mounting bracket, respectively.

The system of any preceding clause, wherein the conduit includes a valveconfigured to adjust a bleed flow through the bleed system, wherein thevalve is disposed between the second and third rotatable joints.

The system of any preceding clause, wherein the mounting bracketincludes first and second mounting arms removably coupled together atmating flanges, the first mounting arm is coupled to the second bleedconduit section, and the second mounting arm is configured to couple tothe wall of the enclosure of the gas turbine engine.

A method includes coupling together, via a first rotatable joint,adjacent conduits of first and second bleed conduit sections of a bleedsystem configured to direct a bleed flow from a compressor section to anexhaust section of a gas turbine engine, wherein the first bleed conduitsection is configured to couple to the compressor section, and thesecond bleed conduit section comprises a set of components configured tocouple to the exhaust section. The method further includes rotating, viathe first rotatable joint, the second bleed conduit section between aplurality of orientations relative to the first bleed conduit sectionand the compressor section, wherein the plurality of orientationscorresponds to a plurality of exhaust outlet orientations of the exhaustsection, and wherein the set of components in the second bleed conduitsection is the same for each orientation of the plurality oforientations.

The method of the preceding clause, wherein the first rotatable jointextends along a central axis of the gas turbine engine, and theplurality of orientations includes different angular orientations aboutthe central axis.

A system includes a compressor section of a gas turbine engine, anexhaust section of the gas turbine engine, and a bleed system configuredto direct a bleed flow from the compressor section to the exhaustsection. The bleed system includes a first bleed conduit section coupledto the compressor section, a second bleed conduit section coupled to theexhaust section, and a first rotatable joint coupling together adjacentconduits of the first and second bleed conduit sections. The secondbleed conduit section is configured to rotate between a plurality oforientations relative to the first bleed conduit section and thecompressor section via the first rotatable joint, wherein the pluralityof orientations corresponds to a plurality of exhaust outletorientations of the exhaust section, and wherein the set of componentsin the second bleed conduit section is the same for each orientation ofthe plurality of orientations.

The system of the preceding clause, wherein the first rotatable jointextends along a central axis of the gas turbine engine, and theplurality of orientations includes different angular orientations aboutthe central axis.

This written description uses examples to disclose the invention,including the best mode, and also to enable any person skilled in theart to practice the invention, including making and using any devices orsystems and performing any incorporated methods. The patentable scope ofthe invention is defined by the claims and may include other examplesthat occur to those skilled in the art. Such other examples are intendedto be within the scope of the claims if they have structural elementsthat do not differ from the literal language of the claims, or if theyinclude equivalent structural elements with insubstantial differencesfrom the literal language of the claims.

The invention claimed is:
 1. A system, comprising: a bleed systemconfigured to direct a bleed flow from a compressor section to anexhaust section of a gas turbine engine, wherein the bleed systemcomprises: a first bleed conduit section configured to couple to thecompressor section; a second bleed conduit section having a portionconfigured to couple to a wall of an exhaust plenum of the exhaustsection, wherein the exhaust plenum comprises an exhaust outletdownstream from the second bleed conduit section; and a first rotatablejoint coupling together adjacent conduits of the first and second bleedconduit sections, wherein the second bleed conduit section comprises aset of components configured to rotate via the first rotatable jointbetween a plurality of orientations relative to the first bleed conduitsection, the compressor section, and the exhaust section, wherein theplurality of orientations are configured to align the portion of thesecond bleed conduit section with a plurality of opening positions alongthe wall of the exhaust plenum, wherein the plurality of orientationscorresponds to a plurality of exhaust outlet orientations of the exhaustoutlet of the exhaust plenum.
 2. The system of claim 1, wherein arotational axis of the first rotatable joint extends along a centralaxis of the gas turbine engine, the plurality of orientations comprisesdifferent angular orientations of the second bleed conduit section andthe plurality of opening positions about the central axis andcircumferentially offset from one another along the wall of the exhaustplenum, the plurality of exhaust outlet orientations of the exhaustoutlet comprise different angular orientations of the exhaust outletabout the central axis and circumferentially offset from one another,and the portion of the second bleed conduit section is radially offsetfrom the rotational axis.
 3. The system of claim 1, comprising the gasturbine engine having the compressor section, the exhaust section, aturbine section, and a combustor section, wherein the exhaust sectioncomprises a plurality of openings in the wall of the exhaust plenumcorresponding to the plurality of opening positions, wherein theplurality of openings are spaced apart from one another along the wall.4. The system of claim 1, wherein each of the plurality of exhaustoutlet orientations of the exhaust outlet is oriented crosswise to acentral axis of the gas turbine engine.
 5. The system of claim 1,wherein the plurality of exhaust outlet orientations of the exhaustoutlet comprises at least two of a left-hand exhaust orientation of theexhaust outlet, a right-hand exhaust orientation of the exhaust outlet,or a top exhaust orientation of the exhaust outlet.
 6. The system ofclaim 1, wherein the plurality of opening positions comprise at least aleft-hand opening position and a right-hand opening position along thewall of the exhaust plenum.
 7. The system of claim 1, wherein the firstbleed conduit section comprises a U-shaped conduit configurationextending at least partially circumferentially about the compressorsection relative to a central axis of the gas turbine engine.
 8. Thesystem of claim 7, wherein the U-shaped conduit configuration comprisesa central straight conduit extending between first and second bendingconduits, the central straight conduit extends crosswise to the centralaxis, the first rotatable joint extends along the central axis, and thecentral straight conduit is coupled to the first rotatable joint.
 9. Thesystem of claim 8, wherein the first bleed conduit section comprises aplurality of gimbals disposed along one or more of the central straightconduit, the first bending conduit, or the second bending conduit. 10.The system of claim 8, wherein the second bleed conduit sectioncomprises a J-shaped conduit configuration extending from the firstrotatable joint to the portion coupled to the wall of the exhaustplenum.
 11. The system of claim 10, wherein the second bleed conduitsection comprises one or more gimbals and one or more spring hangers.12. The system of claim 11, wherein the second bleed conduit sectioncomprises a staged expansion conduit having a plurality of expandingconduits arranged in stages along a direction of a bleed flow throughthe bleed system.
 13. The system of claim 11, wherein the second bleedconduit section comprises a mounting bracket configured to mount thesecond bleed conduit section to an enclosure wall of an enclosure of thegas turbine engine.
 14. The system of claim 13, wherein the second bleedconduit section comprises a second rotatable joint and a third rotatablejoint disposed along a conduit of the second bleed conduit sectionupstream and downstream of the mounting bracket, respectively.
 15. Thesystem of claim 14, wherein the conduit comprises a valve configured toadjust a bleed flow through the bleed system, wherein the valve isdisposed between the second and third rotatable joints.
 16. The systemof claim 14, wherein the mounting bracket comprises first and secondmounting arms removably coupled together at mating flanges, the firstmounting arm is coupled to the second bleed conduit section, and thesecond mounting arm is configured to couple to the enclosure wall of theenclosure of the gas turbine engine.
 17. A method, comprising: couplingtogether, via a first rotatable joint, adjacent conduits of first andsecond bleed conduit sections of a bleed system configured to direct ableed flow from a compressor section to an exhaust section of a gasturbine engine, wherein the first bleed conduit section is configured tocouple to the compressor section, and the second bleed conduit sectioncomprises a set of components and a portion configured to couple to awall of an exhaust plenum of the exhaust section, wherein the exhaustplenum comprises an exhaust outlet downstream from the second bleedconduit section; and rotating, via the first rotatable joint, the secondbleed conduit section between a plurality of orientations relative tothe first bleed conduit section, the compressor section, and the exhaustsection, wherein the plurality of orientations are configured to alignthe portion of the second bleed conduit section with a plurality ofopening positions along the wall of the exhaust plenum, wherein theplurality of orientations corresponds to a plurality of exhaust outletorientations of the exhaust outlet of the exhaust plenum, and whereinthe set of components in the second bleed conduit section is the samefor each orientation of the plurality of orientations.
 18. The method ofclaim 17, wherein a rotational axis of the first rotatable joint extendsalong a central axis of the gas turbine engine, the plurality oforientations comprises different angular orientations of the secondbleed conduit section and the plurality of opening positions about thecentral axis and circumferentially offset from one another along thewall of the exhaust plenum, and the plurality of exhaust outletorientations of the exhaust outlet comprise different angularorientations of the exhaust outlet about the central axis andcircumferentially offset from one another, and the portion of the secondbleed conduit section is radially offset from the rotational axis.
 19. Asystem, comprising: a compressor section of a gas turbine engine; anexhaust section of the gas turbine engine; and a bleed system configuredto direct a bleed flow from the compressor section to the exhaustsection, wherein the bleed system comprises: a first bleed conduitsection coupled to the compressor section; a second bleed conduitsection having a portion coupled to a wall of an exhaust plenum of theexhaust section, wherein the exhaust plenum comprises an exhaust outletdownstream from the second bleed conduit section; and a first rotatablejoint coupling together adjacent conduits of the first and second bleedconduit sections, wherein the second bleed conduit section is configuredto rotate via the first rotatable joint between a plurality oforientations relative to the first bleed conduit section, the compressorsection, and the exhaust section, wherein the plurality of orientationsare configured to align the portion of the second bleed conduit sectionwith a plurality of opening positions along the wall of the exhaustplenum, wherein the plurality of orientations corresponds to a pluralityof exhaust outlet orientations of the exhaust outlet of the exhaustplenum, and wherein a set of components in the second bleed conduitsection is the same for each orientation of the plurality oforientations.
 20. The system of claim 19, wherein a rotational axis ofthe first rotatable joint extends along a central axis of the gasturbine engine, the plurality of orientations comprises differentangular orientations of the second bleed conduit section and theplurality of opening positions about the central axis andcircumferentially offset from one another along the wall of the exhaustplenum, the plurality of exhaust outlet orientations of the exhaustoutlet comprise different angular orientations of the exhaust outletabout the central axis and circumferentially offset from one another,and the portion of the second bleed conduit section is radially offsetfrom the rotational axis.